CN105173121A - Double-helix inflatable deployment type spinning-stability reduction aircraft - Google Patents
Double-helix inflatable deployment type spinning-stability reduction aircraft Download PDFInfo
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- CN105173121A CN105173121A CN201510607309.1A CN201510607309A CN105173121A CN 105173121 A CN105173121 A CN 105173121A CN 201510607309 A CN201510607309 A CN 201510607309A CN 105173121 A CN105173121 A CN 105173121A
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- double helix
- annulus
- gas
- flight device
- spin stabilization
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Abstract
The invention discloses a double-helix inflatable deployment type spinning-stability reduction aircraft. The spinning-stability reduction aircraft comprises a rigid spherical nose cone, an inflatable circular-ring resistance surface, a sectional type diaphragm, a high-pressure gas cylinder, a pressure decompression valve, a guide tube and a cylindrical load box. The double-helix inflatable deployment type spinning-stability reduction aircraft provided by the invention is initially in a collapsed state; and when the aircraft reaches a predetermined rail, the pressure decompression valve is started, the high-pressure gas cylinder in the rigid nose cone starts inflating gas, and two spiral gas-inflating rings sequentially pass through the inner diaphragm to spirally ascend, expand, stretch and form. By virtue of ring slots between adjacent two spiral circular rings which are symmetrical clockwise (or anticlockwise) with a difference of 180 degrees, the structure spins up by virtue of aerodynamic force generated by detour-flow gas, so that the stability problem in a process that an inflatable deployment type reduction aircraft structure flies to enter or re-enter is solved; meanwhile, the resistance area of the structure is greatly improved by virtue of an inflatable deployment part, so that the reduction of the aircraft structure is effectively realized, and recycling of the load box is completed.
Description
Technical field
The present invention relates to a kind of double helix gas-filled unfolded spin stabilization decelerating flight device, belong to aerospacecraft variable configuration field of structural design.
Background technology
CN104290921A discloses a kind of inflating expanded aerodynamic damping reducer structure, and this gas-filled unfolded decelerating flight device exists flight course self and can not work the shortcoming of revolving, and can not realize Stability theory, easily produces the problem of Structure Attitude rolling.
Summary of the invention
Exist self can not rise revolve and flight course unsteady attitude problem to solve existing gas-filled unfolded decelerating flight device technology, the invention provides a kind of double helix gas-filled unfolded spin stabilization decelerating flight device.
The object of the invention is to be achieved through the following technical solutions:
A kind of double helix gas-filled unfolded spin stabilization decelerating flight device, comprise the spherical nose cone of rigidity, inflation annulus resistance area, sectional type barrier film, high-pressure gas bottle, solution pressure valve, conduit, cylindrical load box, described inflation annulus resistance area is the double helix shape be made up of double helix annulus, double helix annulus inside is provided with sectional type barrier film, cylindrical load box is positioned at decelerating flight device inside and is connected with the spherical nose cone of rigidity, high-pressure gas bottle is provided with in the spherical nose cone of rigidity, high-pressure gas bottle is connected with conduit through separating pressure valve, and conduit is connected with double helix annulus.
Double helix provided by the invention gas-filled unfolded spin stabilization decelerating flight device is initially in rounding state, arrive planned orbit, start and separate pressure valve, the high-pressure gas bottle in rigidity nose cone starts inflation, and two screw-shaped inflation rings launch shaping by internal diaphragm spiral escalation expansion successively.According to the annular groove of adjacent of two differences, 180 ° of cw (or conter clockwise) symmetric helix annulus, make the aerodynamic force streaming gas generation that structure is risen to revolve, solve the flight of gas-filled unfolded decelerating flight device structure and enter or reenter stability problem in process; The drag area of structure is significantly promoted by inflating expanded part simultaneously, effectively achieves Flight Vehicle Structure and slows down, complete the recovery of load box.
Accompanying drawing explanation
Fig. 1 is gas-filled unfolded decelerating flight device double helix design figure;
Fig. 2 is double helix gas-filled unfolded decelerating flight device structural entity design drawing;
Fig. 3 is the structural representation of the gas-filled unfolded decelerating flight device of double helix;
Fig. 4 is gas-filled unfolded double helical loop inner septum design drawing;
Fig. 5 is the annular groove of gas-filled unfolded double helix spin stabilization.
Detailed description of the invention
Below in conjunction with accompanying drawing, technical scheme of the present invention is further described; but be not limited thereto; everyly technical solution of the present invention modified or equivalent to replace, and not departing from the spirit and scope of technical solution of the present invention, all should be encompassed in protection scope of the present invention.
As described in Fig. 1-5, double helix provided by the invention gas-filled unfolded spin stabilization decelerating flight device is made up of the spherical nose cone of rigidity 1, inflation annulus resistance area 2, sectional type barrier film, high-pressure gas bottle 3, solution pressure valve 4, conduit 9, cylindrical load box 8 seven part, wherein:
Described inflation annulus resistance area is the double helix shape be made up of double helix annulus, wherein: double helix annulus is made up of A spiral annulus 5 and B spiral annulus 6, and central axis has identical conical helix, and starting point differs 180 °.Its equation is:
x＝ρsinα
0cosθ
y＝ρsinα
0sinθ
z＝ρcosα
0
In formula: α
0for the half of circular cone drift angle, β is helical angle, ρ
0for the initial radium with rigidity nose cone junction helical ring, x, y, z is respectively three locus coordinates of helical ring axis, wherein helical angle 10 °≤β≤30 °.
In the present invention, after spin stabilization decelerating flight device is inflating expanded coning, semiapex angle 45 °≤α
0≤≤75 °.
In the present invention, each spiral 2m of double helix annulus forming inflation annulus resistance area encloses, 3≤m≤6.
In the present invention, the double helix annulus forming inflation annulus resistance area has identical cross-section diameter d, wherein 1/40≤d/D≤3/80, and D is the bore of retarder afterbody.
In the present invention, double helix annulus is made up of flexible fabric Foldable material, mainly contains four layers, is respectively air-retaining liner, bearing layer, thermal insulation layer and heat shield from inside to outside, wherein: air-retaining liner is thin polyurethane film material after thickness 20 microns, and bearing layer is kevlar fabric after 50 microns; Thermal insulation layer is the alumina aerogels of thickness about 1250 microns, and heat shield is the boron fiber of 40 microns.
In the present invention, rigidity spherical nose cone 1 inner high voltage gas cylinder 3, after separating pressure valve 4 and opening, flows in the symmetrical double helix annulus of difference 180 ° through conduit 9 respectively, by realizing progressively launching at vertex of a cone airing form.
In the present invention, there is sectional type barrier film the double helix annulus inside forming inflation annulus resistance area, and described sectional type barrier film is made up of 2n flexible fabric material barrier film 7, and 2n barrier film 7 forms 2 (n+1) air cavity (n is positive integer), every 360 degree of the first and second helical layer annulus wherein from nose cone arrange a barrier film 7, spiral annulus every 90 degree of barrier films 7 afterwards, each barrier film 7 is spiral annulus cross-sectional planes, and all there is a perforation center, the diameter in hole is 1/6 ~ 1/10 of annulus cross-sectional diameter, effect flows in segmentation air cavity can add up air pressure from high-pressure gas bottle 3, the air cavity flow through fully is expanded expansion, another effect be air-flow flow out barrier film 7 become minor diameter perforation time, flow velocity can increase, it penetrates a rear air cavity, promote a rear air cavity development rate, and spiral annulus can be realized to expand in a spiral manner expansion, improve expansion order, and the momentum of gas can also play spin-up to facilitation to structure.
In the present invention, cross-sectional diameter is the double helix annulus of d, with nose cone and afterbody, have two to become the ring part of 0 from diameter D, the angle corresponding to it is 180 degree.Its effect forms flat ring, fully can be connected with nose cone; Also can ensure that afterbody puts down annular uniformly aerodynamic force simultaneously.
In the present invention, the annular groove 10 according to adjacent of two differences, 180 ° of cw (or conter clockwise) symmetric helix annulus makes to stream aerodynamic force that gas produces and structure is risen revolve.Described annular groove 10 is two semicircle cambered surfaces that angle at the beginning difference 180 degree of spiral annulus with cross-sectional diameter intersect, and two circular arcs intersected are spiralling.
Claims (10)
1. a double helix gas-filled unfolded spin stabilization decelerating flight device, it is characterized in that described spin stabilization decelerating flight device is by the spherical nose cone of rigidity, inflation annulus resistance area, sectional type barrier film, high-pressure gas bottle, separate pressure valve, conduit, cylindrical load box is formed, wherein: inflation annulus resistance area is made up of double helix annulus, double helix annulus inside is provided with sectional type barrier film, cylindrical load box is positioned at decelerating flight device inside and is connected with the spherical nose cone of rigidity, high-pressure gas bottle is provided with in the spherical nose cone of rigidity, high-pressure gas bottle is connected with conduit through separating pressure valve, conduit is connected with double helix annulus, the central axis of described double helix annulus has identical conical helix, starting point differs 180 °, its equation is:
x＝ρsinα
0cosθ
y＝ρsinα
0sinθ
z＝ρcosα
0；
In formula: α
0for the half of circular cone drift angle, β is helical angle, ρ
0for the initial radium with rigidity nose cone junction helical ring, x, y, z is respectively three locus coordinates of helical ring axis.
2. double helix according to claim 1 gas-filled unfolded spin stabilization decelerating flight device, it is characterized in that described double helix annulus is made up of flexible fabric Foldable material, mainly contain four layers, be respectively air-retaining liner, bearing layer, thermal insulation layer and heat shield from inside to outside.
3. double helix according to claim 2 gas-filled unfolded spin stabilization decelerating flight device, it is characterized in that described air-retaining liner is thin polyurethane film material after thickness 20 microns, bearing layer is kevlar fabric after 50 microns; Thermal insulation layer is the alumina aerogels of thickness 1250 microns, and heat shield is the boron fiber of 40 microns.
4. double helix according to claim 1 gas-filled unfolded spin stabilization decelerating flight device, is characterized in that described 1 °≤β≤30 °, 45 °≤α
0≤ 75 °.
5. double helix according to claim 1 gas-filled unfolded spin stabilization decelerating flight device, it is characterized in that described spin stabilization decelerating flight device inflating expanded after coning.
6. double helix according to claim 1 gas-filled unfolded spin stabilization decelerating flight device, is characterized in that each spiral 2m of described double helix annulus encloses, 3≤m≤6.
7. double helix according to claim 1 gas-filled unfolded spin stabilization decelerating flight device, it is characterized in that described double helix annulus has identical cross-section diameter d, 1/40≤d/D≤3/80, D is the bore of retarder afterbody.
8. double helix according to claim 1 gas-filled unfolded spin stabilization decelerating flight device, is characterized in that described sectional type barrier film is made up of 2n flexible fabric material barrier film, and 2n barrier film forms 2 (n+1) air cavity, and n is positive integer; Every 360 degree of the first and second helical layer annulus wherein from nose cone arrange a barrier film, afterwards spiral annulus every 90 degree of barrier films, and each barrier film is spiral annulus cross-sectional plane, and all there is a perforation center.
9. double helix according to claim 8 gas-filled unfolded spin stabilization decelerating flight device, is characterized in that the diameter of described perforation is 1/6 ~ 1/10 of annulus cross-sectional diameter.
10. double helix according to claim 8 gas-filled unfolded spin stabilization decelerating flight device, it is characterized in that described double helix annulus with nose cone and afterbody, have two to become the ring part of 0 from diameter D, the angle corresponding to it is 180 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510607309.1A CN105173121B (en) | 2015-09-22 | 2015-09-22 | Double-helix inflatable deployment type spinning-stability reduction aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510607309.1A CN105173121B (en) | 2015-09-22 | 2015-09-22 | Double-helix inflatable deployment type spinning-stability reduction aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105173121A true CN105173121A (en) | 2015-12-23 |
| CN105173121B CN105173121B (en) | 2017-01-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510607309.1A Active CN105173121B (en) | 2015-09-22 | 2015-09-22 | Double-helix inflatable deployment type spinning-stability reduction aircraft |
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|---|---|
| CN (1) | CN105173121B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106494650A (en) * | 2016-11-18 | 2017-03-15 | 上海宇航系统工程研究所 | A kind of reentry vehicle of utilization liquid evaporation inflated type |
| CN111017262A (en) * | 2019-11-28 | 2020-04-17 | 北京空间机电研究所 | Inflatable reentry deceleration flexible unfolding structure folding and unfolding method |
Citations (5)
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|---|---|---|---|---|
| US6607166B1 (en) * | 2002-08-06 | 2003-08-19 | Astrium Gmbh | Inflatable flying body for the rescue descent of a person |
| CN201920788U (en) * | 2010-11-24 | 2011-08-10 | 上海英诺伟微创医疗器械有限公司 | Spirally involute shield type concealed inner mirror channel for enterocoelia minimally invasive surgeries |
| CN102730203A (en) * | 2012-07-10 | 2012-10-17 | 西北工业大学 | Reentry inflation cover with controllable direction |
| CN104290921A (en) * | 2014-09-11 | 2015-01-21 | 哈尔滨工业大学 | Pneumatic damping speed reducer structure capable of being unfolded through air inflation |
| CN104691791A (en) * | 2015-03-28 | 2015-06-10 | 哈尔滨工业大学 | Elastically-expansible multi-tube spiral inflatable gripper |
-
2015
- 2015-09-22 CN CN201510607309.1A patent/CN105173121B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6607166B1 (en) * | 2002-08-06 | 2003-08-19 | Astrium Gmbh | Inflatable flying body for the rescue descent of a person |
| CN201920788U (en) * | 2010-11-24 | 2011-08-10 | 上海英诺伟微创医疗器械有限公司 | Spirally involute shield type concealed inner mirror channel for enterocoelia minimally invasive surgeries |
| CN102730203A (en) * | 2012-07-10 | 2012-10-17 | 西北工业大学 | Reentry inflation cover with controllable direction |
| CN104290921A (en) * | 2014-09-11 | 2015-01-21 | 哈尔滨工业大学 | Pneumatic damping speed reducer structure capable of being unfolded through air inflation |
| CN104691791A (en) * | 2015-03-28 | 2015-06-10 | 哈尔滨工业大学 | Elastically-expansible multi-tube spiral inflatable gripper |
Non-Patent Citations (1)
| Title |
|---|
| 卫剑征等: "充气式再入减速器研究最新进展", 《宇航学报》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106494650A (en) * | 2016-11-18 | 2017-03-15 | 上海宇航系统工程研究所 | A kind of reentry vehicle of utilization liquid evaporation inflated type |
| CN111017262A (en) * | 2019-11-28 | 2020-04-17 | 北京空间机电研究所 | Inflatable reentry deceleration flexible unfolding structure folding and unfolding method |
| CN111017262B (en) * | 2019-11-28 | 2021-07-13 | 北京空间机电研究所 | Inflatable reentry deceleration flexible unfolding structure folding and unfolding method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105173121B (en) | 2017-01-25 |
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